Turbines



0. THElME R May 28, 1963 TURBINES Filed June 8. 1960 0. THElMER May 28,1963 TURBINES 7 Sheets-Sheet 3 Filed June 8, 1960 INVENTOR. @rm% May 28,1963 Filed June 8, 1960 O. THEIMER TURBINES 7 Sheets'-Sheet 4 IN V ENTOR.

May 28, 1963 Filed June 8, 1960 O. THEIMER TURBINES 7 Sheets-Sheet 5 Elk0. THEIMER May 28, 1963 TURBINES Filed June 8. 1960 7 Sheets-Sheet 6 o.THEIMER 3,091,429

TURBINES 7 Sheets-Sheet 7 May 28, 1963 Filed June a. 1960 I ENTOR. 49 mUnited States Patent Ofi Patented May 28, 1963 ice sperms TURBENES OscarTheimer, 35 Fort Washington Ave, 43, New York, N.Y. Filed June 8, 1960,Ser. No. 34,766 3 Claims. (Cl. 253-39.15)

This invention refers to improvements relating to turbines, inparticular to the tunbine rotor as disclosed in my US. Patent No.2,542,549 issued October 3, 1950, and to further improvements disclosedin my application Serial No. 450,180 filed August 16, 1954, nowabandoned, and especially to my improvements disclosed in my applicationSerial No. 731,760 filed April 29, 1958, now Patent No. 3,026,036granted March 20, 1962.

It is a primary object of this invention to provide means considerablysimplifying and strengthening the rotor construction whilesimultaneously greatly reducing the weight and size thereof andimproving the safety of performance.

It is another object of the invention to provide means contributing to ahighly efiicacious and economical turbine construction which is simpleand easy to assemble and disassemble.

These and other objects and advantages of this present invention willbecome more apparent as the following description thereof progresses,which is illustrated in the attached 7 sheets of drawings, in which:

FIG. 1 is a horizontal section of the turbine pursuant to the inventionin which the injection nozzles are located in two separate groups alongthe outer periphery.

FIG. 2 is a vertical sectional view of the turbine seen in FIG. 1.

FIG. 3 is a horizontal section of a modification of the turbine in whichthe injection nozzles are located only on one side along the outerperiphery of the rotor.

FIG. 3a is a horizontal section of another form of the turbine, in whichthe injection nozzles are located in two opposite separate groups alongthe outer rotor periphery.

FIG. 4 is a fragmentary sectional view of a part of the rotor, thesection being taken along line 4-4 of FIG. 5.

FIG. 4a is a fragmentary sectional view of a part of the rotor usingtubes in place of blades.

'FIG. 5 is a perspective view of the rotor, portions of rotor top discare cut out to facilitate inside view of the rotor for clarity sake.

FIG. 6 is a horizontal view of another modification, embodying injectionnozzles located all around the outer periphery.

FIG. 7 is a vertical sectional view taken along lines 77 of FIG. 6.

Referring more particularly to the drawings, FIGS. 1, 2 and 3 illustratepreferred embodiments of the invention, in which the flow of powermedium is guided in almost straight direction from nozzles 40 located inturbine housing 3 through power medium canals 17 into a rotatable innerguide body 4 or chamber 18a, also called guide body drum of rotor 1 ashereinafter in detail described.

In FIGURE 1 the performance of the power medium circulating through therotor takes place in the following manner:

The power medium expelled from the nozzles located in two oppositegroups around the outer rotor periphery circulating in oppositedirection through the adjoining rotating gas canals 17 exerts inaddition to impulse and pressure, also useful friction by action on therotor in direction of rotation during passage through said gas canals17.

The power medium expelled from said gas canals 17 into the rotatinginner guide body 4, respectively, guide chamber 13a which is divided :bypartition walls 5%, 53b to prevent whirl or eddy currents within guidepockets 52, 53 exerts again impulse by reaction on the rotor in rotatingdirection thereof, the power medium ejected from the inner guide body 4into the inner canal ends of the remaining bypassing gas canals :17exerting again impulse by pressure and useful friction by action on therotor in rotating direction thereof during passage through said gascanals 17. The power medium expelled at the outer rotor periphery fromsaid rotor gas canals 17 at its outer canal ends exerts again impulse byreaction similar to jet reaction on account of expansion, pressure,useful friction and centrifugal force on the rotor in rotating directionthereof.

The same performance of the circulating power medium takes place throughboth guide pockets 52., 53 of the guide body 4. Both ends of the coolingcanals 19 are at the outer and inner rotor peripheries 1a, 1b sealedwith respective plates 21a, 21b or other means against entry of powermedium. Said gas canals 17 and cooling canals 19 are disposed inalternate sequence between both opposite arranged rotor discs 12a and13a.

In FIGS. 2 and 7 it is shown that in the present invention the rotorconsists only of one section constituted by rotor discs 12a and 13a incontrast to former disclosures of my inventions in which the rotorconsists of 4 discs.

In FIG. 3 the working method is alike the one in FIG. 1, the onlydifference between these modifications is, that in FIG. 3, the nozzlesare as shown located in one large group on one side along the outerrotor periphery, further that the fiow of gas expelled from said onegroup of nozzles is circulating in one direction through the rotor. Theguide body 4 has no partition walls.

In FIG. 3a it is shown that the nozzles are also located in two oppositegroups along the outer rotor periphery, or if preferred may also bedisposed all around the outer rotor periphery 1:1 as can be seen in FIG.6. The canals ends of the rotor cooling canals 19 are at the inner rotorperiphery 1b sealed by plates 21:: or other means against entry of powermedium from within the inner guide body 4. These rotor cooling canals 19are at the outer rotor periphery 1a adjoining the nozzles 441' sealedwith plates 21b or other means to prevent entry of power medium intosaid cooling canals 19 expelled from the nozzles.

The rotor gas canals 17 and the rotor cooling canals 19 are disposed inalternate sequence between both opposite arranged rotor discs. As in allother modifications, the respective portions of both rotor discs 12a,13a form simultaneously the outer portions of the rotor gas canals 1'7and the rotor cooling canals 19.

The outer portions of the rotor cooling canals 19 which constituteaccordingly respective portions of both rotor discs 12a, 13a areprovided near the inner rotor periphery 1b, with respective openings 19afor inlet of cooling air from the atmosphere on account of automaticsuction taking place during rotation. Said rotor cooling canals 19 areprovided near the outer rotor periphery 1a with openings 1% for outletof said cooling air (FIGS. 1, 3, 3a).

The respective portions of said rotor discs 12a, 13a being respectiveportions of said rotor gas canals 1'7 and rotor cooling canals 1?, arein continuous contact with the ambient atmospheric air for coolingeffect.

The flow of gas expelled from the nozzles into the rotor gas canals 17is circulating therethrough radially in the direction of the inner rotorperiphery 1b.

The inner guide body 4, respectively chamber 18a FIG. 3a between theinner rotor periphery 1b and the sleeve 34b surrounding shaft '2 is onone side in axial direction open for exhaust of gas, because the centerportion of rotor disc 13a is eliminated in the same way as seen in rotordisc 13a of FIG. 7, while rotor disc 12a is closed by its center portionas seen in FIG. 2.

Said chamber 18a within the rotor center is separated by partition guidewalls 52c, 52d, 53c, 53d (FIG. 3a), in order that the gas flow expelledfrom the nozzles 4%) into the adjoining gas canals 17 and from thereinto said chamber 18a is directed therefrom in axial direction into theopen atmosphere.

The purpose of this peculiar arrangement according to FIG. 3a, designedfor stationary turbines is to prevent re-entry of the power medium intothe remaining opposite rotating gas canals 17 extending from the innerrotor periphery 11a towards the outer rotor periphery 1b in order toprevent passage of the power medium through, what would be then, asecond turbine stage, further to achieve a longer cooling period for thehot rotor gas canals 17 before they receive the next charge of hot powermedium. The present simplified new turbine rotor consists instead ofthree rotor sections in axial direction constituted of four rotor discs,as employed in my previous turbine inventions, only of a single rotorsection, constituted of two rotor discs 12a, 13a, which formed in theprevious turbines the rotor middle section, containing the rotor gascanals 17 and the rotor cooling canals 19 disposed in alternate sequencebetween said two rotor discs 12a, 13a (FIGS. 2, 5, 7).

As shown in my Patents Nos. 2,524,549 or 2,783,964 the two previouslyemployed outer rotor cooling sections 0.8. have been eliminated in thispresent simplified new turbine rotor by removing the two outer rotordiscs 12, 13 and further are eliminated the spaced rotor blades C,located between each of the two outer rotor cooling sections.

If preferred, the two outer gas trap sealing devices 24 at the outerrotor periphery (FIGS. 2 and 7) constituted by extensions 22 of rotordiscs 12a, 13a and annular grooves located within housing 3, could alsobe eliminated and replaced with customary turbine sealing devices; noz-Zles 40 which are located within turbine housing 3 extend partiallybetween extensions 22 of rotor discs 12a, 13a (FIGS. 2 and 7).

Said present simplified turbine rotor is constituted by said respectivetwo opposite disposed rotor discs 12a, 13a which are secured to rotorshaft 2 in predetermined axial distance and which comprise therebetweenspaced rotor blades C, constituting respective rotor power canals 17 androtor cooling canals 19 (FIGS. 2, 5, 7).

Said rotor power or gas canals 17 and said cooling or air canals 19 arealso called rotor power medium directing means, respectively rotorcooling medium directing means, and are accordingly constituted by saidboth opposite disposed rotor discs 120, 13a and the therebetweendisposed spaced rotor blades C, defining conveying means, forming innerportions of said rotor canals 17 and 19 (FIGS. 2, 4a, 5 and 7).

Respective portions of said rotor discs constitute the outer parts ofsaid cooling canals 19 of which each one as before described is providednear the inner rotor periphery 1b with openings 19a for inlet, and nearthe outer rotor periphery 1a with openings 1% for outlet (FIGS. 1, 3,3a, 4, 6), or if preferred each cooling canal with one sufiicient largeopening for inlet and outlet of said cooling medium (FIG. 4).

Sealing plates 21b are shown and indicated at the outer rotor periphery(FIG. 5) by dotted lines and sealing plates 21a and 21b at FIGS. 1, 3,3a, 4 and 6 at the outer and inner rotor peripheries by hatched lines.

Power medium and cooling medium are each separately circulating throughsaid respective rotor canals, constituting a rotating enclosure for flowof said respective power medium and cooling medium. Said rotatingenclosure is revolving within a stationary turbine housing or casing 3(FIGS. 1, 2, 3, 3a, 6 and 7).

The outer parts of rotor cooling canals and power medium canals beingportions of both rotor discs 12a, 13a said outer parts respectivelyouter walls of rotor cooling canals 119 including said openings 19a, 1%which are in continuous direct contact with the ambient atmospheric airallowing by means of suction through openings 19::

near the inner rotor periphery entering of atmospheric air, which latterthen is circulating along rotor blades C towards openings 1% near theouter rotor periphery 1a, cooling thereby very efliciently the side byside of the cooling canals 19 adjacent located gas canals 17, to be thenexpelled by means of expansion and centrifugal force through saidopenings 1% near the outer rotor periphery of said cooling canals 19(FIGS. 1, 3, 3a, 4, 5 and 6). Both types of rotor canals extend fromnear the outer rotor periphery 1a to the inner rotor periphery 1b, thelatter extends circumferentially in some distance from said shaft 2(FIGS. 1, 3, 3a, 5, 6).

Within the inner rotor periphery 1b and the central sleeve 34bsurrounding shaft 2 is provided between the opposite disposed rotordiscs 12a, 13a by means of its center portions a rotatable chamber 18adefined by said rotatable inner guide body 4 (FIGS. 1, 2, 3, 3a, 6 and7) which is modified in FIG. 1 by partition guide walls 52b, 53b inguide pockets 52, 53, constituting a first and second rotatable innerguide body section or if preferred be divided by more than one partitionwall in two or more sections, respectively to form further guide pockets(not shown).

Said rotatable inner guide body 4 respectively chamber 18a isconstituted by said center portions of the rotor discs 12a, 13a and theinner ends of the rotor blades C which terminate at the inner rotorperiphery 1b (FIGS. 1, 2, 3, 3a, 6, 7).

In the modifications of FIGS. 1, 2, 3, 5 the center portions of rotordiscs 12a, 12a are simultaneously parts of the rotatable inner guidebody 4 or chamber 18a, further central sleeve 34b is protecting shaft 2against direct heat contact, as well as protecting the rotor gas canals17 against entry of cooling medium passing through cut outs 37 in thehousing plates 6, 7 and orifices 14b in the rotor discs into and throughsaid central sleeve 3% (FIGS. 2, 7 Said central sleeve 34b (FIGS. 2, 3,3a, 6, 7) is fixedly connected with the center portions of said rotordiscs 12a, 13a and in near distance surrounding shaft 2 and revolvingtherewith, which shaft '2 extends through and beyond rotor discs 12a,13a (FIGS. 2, 7).

Ambient atmospheric air around the rotor discs 12a, 13a enters throughsaid apertures 19a near the inner rotor periphery 1b provided inportions of each one of rotor discs 12a, 13:: being simultaneouslyportions of said rotor cooling canals 19 (FIGS. 1, 3, 3a, 4, 6). Saidair is entering through said apertures 19a into said cooling canals 19and after passing therethrough is expelled out into the atmosphere onaccount of centrifugal force and expansion through apertures 1% near theouter rotor periphery 1a provided within said rotor discs 12a, 13a,respectively within said rotor cooling canals. If instead rotor blades Clocated within rotor discs 12a, 13a rotor tubes are ernployed (FIG.46:), not only saidrotor discs themselves, but also the inserted rotortubes are each to be provided at the corresponding positions on bothopposite portions with at least one substantially large aperture forcirculation of cooling medium.

Referring particularly to FIG. 4 details shown therein are as follows:One of said rotor cooling canals 19 has two apertures 19a, 1%, whereasthe other right hand cooling canal 19 has only a simple large apertureextending from near one canal end to near the other canal end.

FIG. 5 is a perspective view of the present improved turbine rotorincluding rotor power canals 17 open at both ends and rotor coolingcanals 19, covered by plates 21b 0 other means indicated by clottedlines. Portions of one rotor disc are cut out to facilitate for clarityssake inside view of the rotor.

Between rotor discs 12a, 13b are as before mentioned, spaced rotorblades C, forming jointly cooling medium canals and power medium canals,constituting together simultaneously a revolving enclosure, respectivelycasing. Within the respective rotor canals, power medium and coolingmedium are separately circulating in enclosed condition, and arerevolving within the stationary housing 3 (FIGS. 1, 3, 3a and 6).

Performance, proceedings and eifects of the power medium, as well as thecirculation thereof during operation, also the other features within thepresent new rotor pursuant to (FIGS. 1, 2, 3, 3a, 6, 7) are carried outand taking place in the same way as described in application Serial No.731,760, now Patent No. 3,026,086, but with greater efficiency onaccount of the much lighter weight, direct supply of large masses ofatmospheric air and other advantages.

Performance, proceedings and effects of the cooling medium in thepresent new embodiment takes place in almost the same manner and way, asdescribed in application Serial No. 731,760, now Patent No. 3,026,086,with the only exception of variation of the air circulation, because inthe present new simplified rotor construction no rotor outer air coolingsection 0.8. are present, but only a single rotor section includingpower and cooling air canals disposed in alternate sequence, so that thesurrounding ambient air around the rotor discs 12a, 13a enters throughopenings 19a near the inner rotor periphery 1b direct into the rotorcooling canals 19 (FIGS. 1, 3, 3a, 4, 5, 6) instead indirectly by meansof said both rotor outer air cooling sections 0.5. as previouslydisclosed in my aforesaid applications.

The outer walls of the rotor power canals 17 as well as of the rotorcooling canals 19 being portions of the rotor discs 12a, 13a are veryefficiently cooled on account of the high rotor revolution, during whichthe rotor discs with said openings 19a, 1% are cutting through thesurrounding ambient atmospheric air, while in the former rotormodification as shown in my Patents Nos. 2,524,549 or 2,783,964,atmospheric air enters via said openings 19a into said cooling canals 19within the middle rotor section indirect from the rotor cooling canals19 located within said both outer rotor cooling sections O.S.

In consequence of the peculiarly arranged rotor construction, there isno harmful friction of the power medium and the cooling medium with thestationary turbine housing or casing, because the respective circulatingmedia enclosed in the rotor canal do not come in contact therewith,neither develops harmful friction with the rotor canals. On the contrarythere is only as before mentioned useful friction in direction ofrotation of both circulating media with the rotor canal walls, therebyincreasing the driving force, respectively the turbine power output.Therefore very small and insignificant power output is lost in spite ofair suction and air expulsion of huge masses of cooling air circulatingduring rapid revolution of the turbine rotor, but is in three waysalmost fully compensated for, first by impact (action) of the vigorousonrushing air flow entering via openings 37 provided in the housingplates 6, 7 (FIGS. 2, 7) and via opening 1% near the inner rotorperiphery in rotor discs 12a, 13a against the peculiar curved rotorblades C (FIGS. 1, 3, 3a, 5, 6), secondly by impulse and pressure duringthe enormous rapid passage of the cooling air through the rotor coolingcanals 19 and thirdly by repulsion (reaction of the air flow whenexpelled with great contrifugal force from the cooling canals 19 at theouter rotor periphery 1a (FIGS. 1, 2, 3, 3a, 4, 5, 6).

The onrushing air flow against the rotor blades C, respectively rotorcanals is working in a similar manner as the wind striking against theblades of a wind mill.

To increase the efiiciency of cooling the hot rotor power canals 17,freezers, air conditioners or other cooling means (not shown) may bearranged at opposite sides, between the housing plates 6 and 7 and therotor 1, as shown in the application Serial No. 731,760 filed April 29,1958.

The rotor power canals or tubes 17 and the rotor cooling canals or tubes19 are curved, forming preferably a part of an absolute or anapproximate logarithmic spiral. Said rotor canals are curved in thedirection of the rotor movement and curved at opposed ends; thesecurvatures at opposed ends are situated with respect to the inner andouter rotor peripheries in an angle somewhat opposed to the direction ofrotor movement.

In the present instance the rotor canals, tubes or the like aresubstantially oblong and the profile of the gas canals or tubes havethroughout their entire length the same square measurement in order toensure equal flow of power medium.

Due to the fact, that the power and cooling media are simultaneouslymoving in enclosed condition, while passing through the respectiverevolving rotor canals 17, 19 within the turbine casing, contact anddetriment-a1 friction of the power as well as of the cooling medium withthe walls of the stationary turbine casing 3 during their circulationthrough the turbine rotor canals is effectively almost entirelyeliminated.

To achieve the aforesaid and other purposes, the turbine according to myPatent No. 2,524,549 issued October 3, 0, has been improved pursuant tothe present invention and greatly simplified by eliminating all outerguide pockets, the numerous guide members of the inner guide pockets,the inner rotor rim members, the inner stationary guide body beingreplaced by an inner rotating guide body, the stationary sleeve beingreplaced by a rotating sleeve. Further there are eliminated the sleevesupport, some ball-bearings, the inner gas trap sealing devices,constituted by the inner rotor disc extensions and the annular groovesprovided within the inner stationary .guide body.

Further eliminated are the two outer rotor discs 12 and 13 and all rotorblades respectively rotor air cooling canals disposed between rotordiscs 12 and 12b, and 13- and 13b, constituting the rotor cooling canalslocated within both outer rotor cooling sections.

FIGS. 6 and 7 illustrate a modification pursuant the invention for usein airplanes.

Rotor 200 has an open chamber 18a between the inner rotor periphery andthe central sleeve 34b (FIGS. 6, 7) to allow axial passage therethroughof atmospheric air rammed into by means of the airplane nose duringforward flight, as well as to allow exhaust gas ejected from the gascanals 17 running into said open chamber disposed in alternate sequencewith the rotor air cooling canals within the single rotor section, beingin my previous disclosures the rotor middle section. Said cooling canals19 are sealed at opposed ends to prevent entrance of power medium.

The radially extending rotor gas canals 17 are beyond the inner rotorperiphery 1b somewhat extending in axial curved direction into saidrotor chamber 18a towards the plane tail (FIG. 6).

The center portions of rotor discs 12a, 13a, as well as the housingplates 6, 7 have according modification FIGS. 6, 7 large cut outs toprovide openings 37, 14a, 14b to allow abundant air inlet and air andgas outlets according to arrows A and G (FIG. 7).

In FIG. 6 the center portions within the inner rotor periphery 1b ofeither or both rotor discs 12a, 13a may be eliminated, depending whetherthe turbine is used for stationary purposes or for airplanes.

The swift circulating air through the cooling canals 19 are efficientlycooling the adjacent hot Walls of the power medium canals 17,respectively, the rotor blades C.

Said power medium rotor canals 17 being entirely surrounded by coolingmeans, that is partly by the adjacent cooling canals and partly by theambient atmospheric air surrounding the rotor discs 12a, 13a.

The construction of the cooling system and the method of coolingproceedings are in the present modifications identical with the turbinemodifications previously disclosed.

The rotor chamber 18a is pursuant to modification FIGS. 6, 7 not sealedoff by the center portions of rotor discs 12a, 13a, which form in themodifications of FIGS.

2 and 3 portions of the axially sealed rotating inner guide body 4 orchamber 18a intended for radial passage of power medium.

Inmodification (FIGS. 6, 7) said rotor chamber 18a is used for axialpassage of the exhaust gas injected thereintd from the power canals 17together with the atmospheric air rammed into said airplane nose, to bejointly expelled with great force through the tail end of the airplane,adding considerable turbine power output by jetreaction.

In the modification of FIGS. 6, 7, the injection nozzles 40 are disposedall around the entire outer rotor periphery.

On account of the various elirninations and the specific rotorconstruction, undesirable harmful friction is very insignificant,further because of the greatly simplified construction, the turbine isconsiderably reduced in size and'weight and the safety of performance isvery improved.

Means may be provided to overcome various difficulties arising fromdifferent peculiarities of the rotor material used, as are: strain,stress, pull, tension, creep, thermal expansion in consequence of thehigh temperatures of the power medium and the enormous rotor revolution.

Means to overcome said difliculties, are to assemble interchangeably theseparate important rotor parts, such as the rotor discs, rotor blades,strips or tubes and other parts, for instance with: threaded bolts 10%passing through and beyond the repective rotor discs at such placeswhich are not in direct contact with the hot gases.

Said rotor discs are secured to said threaded bolts 1% by nuts 101pressing against very strong special springs 102 or compressed aircushions or other elastic, selfadjusting shock and pressure resistingmeans, permitting expansion and contraction of the rotor material, insuch a manner, that all assembled rotor parts form a compact structure,safely withstanding the high centrifugal force caused by the enormousrotor speed, and all other mentioned forces and ditficulties (FIG. 5).

This new method of assembling, mounting and dismounting of rotorsexchange of rotor parts, repairs, cleaning as well as re-assembling ofrotors is most simple and accomplished in much less time as usual, forinstance by welding, soldering, etc.

The turbine housing, as well as the rotor and its various parts of allmentioned modifications, may if preferred, each be constructed as a unitfrom a casting, or in secrtions made of castings to facilitateassembling of the turbine.

If not detrimental to the compactness, tear-pull and strain resistancerequired of the rotor material on account of said specified difficultiesand forces, for the purpose of furtherimprovements of the coolingcapacity, porous rotor material or such with tiny slots may be used, toenable besides convection also transpiration or film cooling.

The number of power canals 17 and cooling canals 19 may vary and andtheir shapes are preferably oblong.

Number and proportions of dimensions of nozzles, rotor canals,dimensions of the innerguide body, guide pockets, the open spacerespectively chamber of the rotor have to be each calculatedrespectively adapted in conformity with the quantity, pressure and othercharacteristics of the power medium used in the turbine and thenecessities of the power capacity desired, respectively required.

It is well understood in accordance with the above description anddrawings submitted, that deviations and changes may be made from theembodiments herein set forth, without departing from the spirit andscope of this invention.

Having thus described the invention, what is claimed as new and desiredto be secured by Letters Patent, is:

-l. A rotor structure for a turbine comprising two parallel and spacedrotor discs having therebetween a plurality of rotor blades, which arespaced from each other and extend in substantially radial direction fromthe outer periphery to the inner rotor periphery and in axial directionfrom'one of the rotor discs to the other rotor disc, said bladesdefining power medium rotor canals terminating in open ends located atthe outer rotor periphery and at the inner rotor periphery,respectively, said power medium rotor canals being spaced from eachother and defining therebetween cooling medium rotor canals providedwith opposite sealed ends at the inner and outer rotor peripheryrespectively, said cooling medium rotor canals having openingsconstituting an inlet opening for a cooling medium located near theinner rotor periphery and an outlet opening for said cooling mediumlocated near the outer rotor periphery, said cooling medium rotor canalscommunicating directly with the atmosphere through said openings in saidrotor discs.

2. A rotor structure for a turbine comprising two parallel spacedring-shaped rotor discs having an inner rotor periphery and an outerrotor periphery, a sleeve member, power medium rotor manals and coolingmedium rotor canals located in alternate sequence between and defined bysaid parallel spaced rotor discs, said power medium rotor canals andsaid cooling medium rotor canals extending from said inner rotorperiphery to said outer rotor periphery of said rotor discs, said innerrotor pe riphery and said sleeve member forming the boundary of achamber having one open end located in one of said ring shaped rotordiscs and being closed at the face of the other rotor disc and centrallylocated guide walls within said chamber and extending from one side tothe opposite side of said inner rotor periphery, said guide Wallsfacilitating expulsion of combustion gas in axial direction of said onerotor disc when the gas passes said chamber from said power medium rotorcanals.

3. A rotor structure for a turbine comprising two spaced parallel ringshaped rotor discs having an inner rotor periphery and an outer rotoperiphery, a sleeve extending axially and centrally through said discs,radially directed power medium rotor canals and cooling medium rotorcanals located in alternate sequential relationship between said rotordiscs, a chamber bounded by said sleeve and said inner rotor peripheryand being open at both said rotor discs, said cooling medium rotorcanals and said power medium rotor canals extending from said outerrotor periphery to said inner rotor periphery and projecting therefrominto said chamber.

References Cited in the file of this patent UNITED STATES PATENTS1,887,717 Koch Nov. 15, 1932 2,524,549 Theimer Oct. 3, 1950 2,568,726Franz Sept. 25, 1951 2,641,040 Goddard June 9, 1953 2,783,964 TheimerMar. 5, 1957

1. A ROTOR STRUCTURE FOR A TURBINE COMPRISING TWO PARALLEL AND SPACEDROTOR DISCS HAVING THEREBETWEEN A PLURALITY OF ROTOR BLADES, WHICH ARESPACED FROM EACH OTHER AND EXTEND IN SUBSTANTIALLY RADIAL DIRECTION FROMTHE OUTER PERIPHERY TO THE INNER ROTOR PERIPHERY AND IN AXIAL DIRECTIONFROM ONE OF THE ROTOR DISCS TO THE OTHER ROTOR DISC, SAID BLADESDEFINING POWER MEDIUM ROTOR CANALS TERMINATING IN OPEN ENDS LOCATED ATTHE OUTER ROTOR PERIPHERY AND AT THE INNER ROTOR PERIPHERY,RESPECTIVELY, SAID POWER MEDIUM ROTOR CANALS BEING SPACED FROM EACHOTHER AND DEFINING THEREBETWEEN COOLING MEDIUM ROTOR CANALS PROVIDEDWITH OPPOSITE SEALED ENDS AT THE INNER AND OUTER ROTOR PERIPHERYRESPECTIVELY, SAID COOLING MEDIUM ROTOR CANALS HAVING OPENINGSCONSTITUTING AN INLET OPENING FOR A COOLING MEDIUM LOCATED NEAR THEINNER ROTOR PERIPHERY AND AN OUTLET OPENING FOR SAID COOLING MEDIUMLOCATED NEAR THE OUTER ROTOR PERIPHERY, SAID COOLING MEDIUM ROTOR CANALSCOMMUNICATING DIRECTLY WITH THE ATMOSPHERE THROUGH SAID OPENINGS IN SAIDROTOR DISCS.